CN109959926A - A kind of radar altimeter - Google Patents
A kind of radar altimeter Download PDFInfo
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- CN109959926A CN109959926A CN201711418418.4A CN201711418418A CN109959926A CN 109959926 A CN109959926 A CN 109959926A CN 201711418418 A CN201711418418 A CN 201711418418A CN 109959926 A CN109959926 A CN 109959926A
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/882—Radar or analogous systems specially adapted for specific applications for altimeters
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- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
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- Electromagnetism (AREA)
- Computer Networks & Wireless Communication (AREA)
- General Physics & Mathematics (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
A kind of radar altimeter, comprising: radio-frequency front-end: being built-in with radio frequency chip, sends waveform and reception echo for controlling；Arm chip controls radio frequency chip using DAC module in the chip, receives I, Q data by GPIO interface using ADC module, and resolve data feeding CPU by DMA channel；The distance value calculated is carried out data interaction by interface and system for flight control computer and earth station by CPU；External circuit: including clock module, and filter module etc. provides adequate and systematic service for Arm chip；Power module: power supply is provided for this system.It can not only be greatly improved on working efficiency, can also greatly reduce field work, reduce artificial line walking cost.
Description
Technical field
The invention belongs to unmanned plane radar altimeter field, specifically a kind of radar altimeter.
Background technique
Since people's quality of life is continuously improved, domestic power grid constantly expands, long distance powedr transmission network line rapid development,
And many transmission lines of electricity are distributed among a mountain high mountain, for daily electric power maintenance, inspection, prevent and prevent electric power accident hair
The work such as raw need to carry out electric power cable Daily Round Check, inspection.Currently, the working contents of electric power inspection are still by people
Work crosses over mountain after mountain to patrol to existing electric power cable.Heavy workload, it is especially arduous in field and remote mountains.Therefore anxious
A kind of tool is needed to replace manually carrying out fixed high inspection, line walking, to save labour.
Summary of the invention
For disadvantages mentioned above of the existing technology and deficiency, the present invention provides a kind of radar altimeters, not only in work
Make to greatly improve in efficiency, can also greatly reduce field work, reduces artificial line walking cost.
The invention is characterized in that a kind of radar altimeter, comprising:
Radio-frequency front-end: being built-in with radio frequency chip, sends waveform and reception echo for controlling；Arm chip uses the chip
Interior DAC module controls radio frequency chip, receives I, Q data by GPIO interface using ADC module, and pass through DMA channel for data
CPU is sent into be resolved；The distance value calculated is carried out data friendship by interface and system for flight control computer and earth station by CPU
Mutually；
External circuit: including clock module, and filter module etc. provides adequate and systematic service for Arm chip；
Power module: power supply is provided for this system.
Further, radio-frequency front-end further includes receiving antenna and transmission antenna, respectively uses autonomous channel.
Further, CPU carries out data interaction using RS232, CAN bus and iic bus and flight control system, and CPU passes through
2.4GHz WiFi module and earth station carry out data interaction.
Further, above system, further includes:
AD data input module: I, Q data all the way are acquired by the ADC module of Arm chip；
It removes DC Module: each of I, Q data data is individually subtracted with the mean value of respective data summation；
FFT calculates, Threshold detection module: to going the I after direct current, Q data to carry out FFT transform, time domain data being converted into
Frequency domain data, and to the plural modulus after calculating；Frequency domain data is subjected to Threshold detection, finds out threshold point amplitude maximum one
Point；
It resolves spacing module: being calculated according to FFT, Threshold detection module show that upper frequency sweep crosses thresholding maximum point coordinate as up_
Max_index, the corresponding frequency of point are fd_up, and it is down_max_index, the point pair that lower frequency sweep, which crosses thresholding maximum point coordinate,
The frequency answered is fd_down, and then height H is calculated.
Further, above system further include: data processing module carries out data processing to the height H calculated, to reach
To filtering, the purpose of stable data.
Further, height H in spacing module is resolved are as follows:
Wherein C is the light velocity, C=3*108；T is the period；B is modulation bandwidth.
Further, data processing, including filtering processing module are carried out to height H in data processing module, using alpha-beta
Filter, the predictive equation of the constant gain filters are X (k+1/k)=Φ X (k/k), and filtering equations are X (k+1/k+1)=X (k
+ 1/k)+K [Z (k+1)-H (k+1/k)], wherein X (k/k) be the k moment filter value, X (k+1/k) be the k moment to it is next when
The predicted value at quarter, Z (k) are the observations at k moment；
When moving equation uses constant velocity model, constant gain matrix K=[α, β/T]T, state-transition matrixThe measurement matrix of this model is H=[1,0].
Further, α-βfilter meets constant gain matrix K, and state-transition matrix Φ, measurement matrix H are respectively
The constant gain filters of above-mentioned expression formula description, i.e.,
Wherein, 0 < α <, 1,0 < β < 1.
As further, data processing is carried out to height H in data processing module, further includes data smoothing processing mould
Block,
If the long factor of window is Y, adjusted according to data stability, data once enter in window according to first in first out in window
It calculates, the calculating mean value after removing maximum height value and minimum height values in window, obtains output height to the end, calculation formula is such as
Under:
The present invention due to using the technology described above, can obtain following technical effect: can be existed with effective compensation target
The Doppler frequency shift generated in motion process guarantees the accuracy of the unmanned plane distance of altimeter resolving awing.Filtering method
It is combined with drawing window method, improves rejecting of the whole system when height is resolved for data jump, singular value, and increase
Data stability and continuity.System of the invention not only can with earth station's communication interaction data and also will apart from resolve believe
Breath is transmitted to system for flight control computer, and flight control system directly can carry out corresponding data fusion using this range information and resolve in fact
Shi Gaodu.
Detailed description of the invention
The present invention shares 3 width of attached drawing:
Fig. 1 is transmitted waveform schematic diagram；
Fig. 2 is a kind of radar altimeter structural block diagram in embodiment；
Fig. 3 is module class signal processing method flow chart in embodiment.
Specific embodiment
Below with reference to the embodiments and with reference to the accompanying drawing technical scheme of the present invention will be further explained in detail.
The working frequency of radar altimeter involved in the application is in 24GHz, 60GHz or 77GHz, using FMCW continuous wave
FM system.It using FMCW system, is primarily due under this system, distance resolution is higher, is able to satisfy the needs of application scenarios.
Modulation waveform uses symmetric triangular wave, this waveform not only can be with real-time detection unmanned plane when static and measured object, such as ground, it
Between distance, also can real-time detection unmanned plane in flight and measured object, such as ground, the distance between.This equipment can pass through
Multiple communication interface interaction data, can not only be by data distributing to earth station, and data can be reached to unmanned plane and fly control system
The other equipment solution calculated altitude such as the height value of this equipment real-time resolving and GPS, barometer can be carried out data and melted by system, flight control system
Conjunction processing.Data fusion is carried out for flight control system, and one stabilization, accurate data source are provided.
The ranging range of the radar altimeter system of present embodiment is in 1m~50m, distance resolution 0.5m, radar center
Frequency is 24.128GHz, and transmitted waveform uses symmetric triangular wave, period 2ms, bandwidth 300M.Transmitted waveform schematic diagram such as Fig. 1
It is shown.
Embodiment 1
The present embodiment provides a kind of radar altimeters, comprising:
Radio-frequency front-end: being built-in with Infineon's radio frequency chip, sends waveform and reception echo for controlling；It transmission antenna and connects
It receives antenna and receives autonomous channel using a hair one；
Arm chip, using in the chip DAC module control radio frequency chip, using ADC module by GPIO interface reception I,
Q data, and resolved data feeding processing module CPU by DMA channel, it is not take up other peripheral clocks；Processing module
CPU carries out related resolving, including FFT is calculated, and height resolves etc., and the distance value calculated is flown into control by interface and unmanned plane
System and earth station carry out data interaction；Preferably, CPU is counted using RS232, CAN bus and iic bus and flight control system
According to interaction, CPU carries out data interaction by 2.4GHz WiFi module and earth station.
RS232 interface: Arm chip output Transistor-Transistor Logic level is converted into 232 level, can use the max3232 chip of MAXIM company
Carry out level conversion.
IIC interface uses the iic bus of Arm chip interior, can be directly connected to exterior I IC bus.
CAN interface: level conversion can be carried out with the MCP2515 chip of MICROCHIP company；
2.4GHz WiFi module: long transmission distance under 2.4GHz frequency range, and strong antijamming capability.
External circuit: including clock module, and filter module etc. provides adequate and systematic service for Arm chip；That is Arm chip operation
When each communication interface support circuit.
Power module: power supply is provided for this system.
Embodiment 2
The present embodiment provides a kind of radar altimeter signal processing methods, resolve radar to measured object by I/Q data all the way
Distance, and upper frequency sweep and lower frequency sweep are to resolve the pre-treating method apart from step identical；
The above method specifically includes:
The input of S1, AD data: I, Q data all the way are acquired by the ADC module of Arm chip；
S2 removes direct current: each of I, Q data data being individually subtracted with the mean value of respective data summation, is made a return journey with this
Except the influence of DC component.
S3, FFT calculate, Threshold detection: to going the I after direct current, Q data to carry out FFT transform, time domain data being converted into frequency
Numeric field data, and to the plural modulus after calculating；Frequency domain data is subjected to CFAR Threshold detection, finds out threshold point amplitude maximum one
A point；It mainly considers to need when unmanned plane during flying relative to ground stability Calculation relative altitude, and radar cross section RCS
It is smaller relative to ground, it took threshold amplitude maximum point to meet calculating when so calculating and required.
S4 resolves distance: showing that upper frequency sweep crosses thresholding maximum point coordinate according to step S3 is up_max_index, the point pair
The frequency answered is fd_up, and it is down_max_index that lower frequency sweep, which crosses thresholding maximum point coordinate, which is fd_
Down, and then height H is calculated:
Wherein C is the light velocity, C=3*108；T is period, T=2ms；B is modulation bandwidth, B=300MHz.
Embodiment 3
As the supplement to embodiment 2, the above method further include: S5 carries out data processing to the height H calculated, this
Step mainly carries out solution calculated altitude post-processing, that is, plays the role of proposing data exception point, smoothed data.
Data processing is carried out to height H in S5, includes the steps that being filtered: using α-βfilter, fixed-gain filter
The predictive equation of device is X (k+1/k)=Φ X (k/k), and filtering equations are X (k+1/k+1)=X (k+1/k)+K [Z (k+1)-H (k+
1/k)], wherein X (k/k) is the filter value at k moment, and X (k+1/k) is the k moment to the predicted value at next moment, and Z (k) is k
The observation at moment；
When moving equation uses constant velocity model, constant gain matrix K=[α, β/T]T, state-transition matrixThe measurement matrix of this model is H=[1,0]；
α-βfilter meets constant gain matrix K, and state-transition matrix Φ, measurement matrix H are respectively that above-mentioned expression formula is retouched
The constant gain filters stated, i.e.,
Wherein, 0 < α <, 1,0 < β < 1.The value of α and β can be calculated according to formula,
I.e.WithWherein k is number, α and β as the variation of k takes different values, practical
In use, the two parameters can tend to definite value.
Data processing is carried out to height H in S5, further includes the steps that data smoothing is handled,
If the long factor of window is Y, adjusted according to data stability, data once enter in window according to first in first out in window
It calculates, the calculating mean value after removing maximum height value and minimum height values in window, obtains output height to the end, calculation formula is such as
Under:
The embodiment improves rejecting of the whole system when height is resolved for data jump, singular value, and increases
Data stability and continuity.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto,
Anyone skilled in the art within the technical scope of the present disclosure, according to the technique and scheme of the present invention and its
Inventive concept is subject to equivalent substitution or change, should be covered by the protection scope of the present invention.
Claims (9)
1. a kind of radar altimeter characterized by comprising radio-frequency front-end: being built-in with radio frequency chip, send waveform for controlling
With reception echo；Arm chip is controlled radio frequency chip using DAC module in the chip, is connect using ADC module by GPIO interface
I, Q data are received, and is resolved data feeding CPU by DMA channel；The distance value calculated is passed through interface and nothing by CPU
Man-machine flight control system and earth station carry out data interaction.
2. a kind of radar altimeter according to claim 1, which is characterized in that radio-frequency front-end further includes receiving antenna and hair
Antennas respectively uses autonomous channel.
3. a kind of radar altimeter according to claim 1 or claim 2, which is characterized in that CPU uses RS232, CAN bus and IIC
Bus and flight control system carry out data interaction, and CPU carries out data interaction by 2.4GHz WiFi module and earth station.
4. a kind of radar altimeter according to claim 1, which is characterized in that above system, further includes:
AD data input module: I, Q data all the way are acquired by the ADC module of Arm chip；
It removes DC Module: each of I, Q data data is individually subtracted with the mean value of respective data summation；
FFT calculates, Threshold detection module: to going the I after direct current, Q data to carry out FFT transform, time domain data being converted into frequency domain
Data, and to the plural modulus after calculating；Frequency domain data is subjected to Threshold detection, finds out the maximum point of threshold point amplitude；
It resolves spacing module: being calculated according to FFT, Threshold detection module show that upper frequency sweep crosses thresholding maximum point coordinate as up_max_
Index, the corresponding frequency of point are fd_up, and it is down_max_index that lower frequency sweep, which crosses thresholding maximum point coordinate, and the point is corresponding
Frequency is fd_down, and then height H is calculated.
5. a kind of radar altimeter according to claim 4, which is characterized in that above system further include: data processing module,
Data processing is carried out to the height H calculated, to achieve the purpose that filtering, stablize data.
6. a kind of radar altimeter according to claim 4, which is characterized in that resolve height H in spacing module are as follows:
Wherein C is the light velocity, C=3*108；T is the period；B is modulation bandwidth.
7. a kind of radar altimeter according to claim 5, which is characterized in that counted in data processing module to height H
According to processing, including filtering processing module, using α-βfilter, the predictive equation of the constant gain filters is X (k+1/k)=Φ X
(k/k), filtering equations are X (k+1/k+1)=X (k+1/k)+K [Z (k+1)-H (k+1/k)], wherein X (k/k) is the k moment
Filter value, X (k+1/k) are the k moment to the predicted value at next moment, and Z (k) is the observation at k moment；
When moving equation uses constant velocity model, constant gain matrix K=[α, β/T]T, state-transition matrixThe measurement matrix of this model is H=[1,0].
8. a kind of radar altimeter according to claim 7, which is characterized in that α-βfilter meets constant gain matrix K,
State-transition matrix Φ, measurement matrix H are respectively the constant gain filters of above-mentioned expression formula description, i.e.,
Wherein, 0 < α <, 1,0 < β < 1.
9. a kind of radar altimeter according to claim 5, which is characterized in that counted in data processing module to height H
It further include data smoothing processing module according to processing,
If the long factor of window is Y, adjusted according to data stability, data once enter in window according to first in first out and count in window
It calculates, the calculating mean value after removing maximum height value and minimum height values in window, obtains output height to the end, calculation formula is such as
Under:
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|---|---|---|---|---|
| CN201191184Y (en) * | 2008-03-11 | 2009-02-04 | 陕西长岭电子科技有限责任公司 | Digital wireless electric height meter |
| CN101968539A (en) * | 2010-09-29 | 2011-02-09 | 中国科学院空间科学与应用研究中心 | Multifunctional digital signal processor for skyborne or spaceborne radar altitude gauge |
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| CN205539456U (en) * | 2016-03-31 | 2016-08-31 | 大连楼兰科技股份有限公司 | A 77GHz millimeter wave radar altimeter for unmanned aerial vehicle |
| CN108107426A (en) * | 2018-01-31 | 2018-06-01 | 菏泽学院 | A kind of radio altimeter |
-
2017
- 2017-12-25 CN CN201711418418.4A patent/CN109959926A/en active Pending
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|---|---|---|---|---|
| CN201191184Y (en) * | 2008-03-11 | 2009-02-04 | 陕西长岭电子科技有限责任公司 | Digital wireless electric height meter |
| CN101968539A (en) * | 2010-09-29 | 2011-02-09 | 中国科学院空间科学与应用研究中心 | Multifunctional digital signal processor for skyborne or spaceborne radar altitude gauge |
| CN105445714A (en) * | 2015-11-24 | 2016-03-30 | 大连楼兰科技股份有限公司 | Automobile forward direction anticollision system signal processing method |
| CN205539456U (en) * | 2016-03-31 | 2016-08-31 | 大连楼兰科技股份有限公司 | A 77GHz millimeter wave radar altimeter for unmanned aerial vehicle |
| CN108107426A (en) * | 2018-01-31 | 2018-06-01 | 菏泽学院 | A kind of radio altimeter |
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| Title |
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Application publication date: 20190702 |